(19)
(11) EP 2 088 288 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
20.04.2016 Bulletin 2016/16

(43) Date of publication A2:
12.08.2009 Bulletin 2009/33

(21) Application number: 09151741.7

(22) Date of filing: 30.01.2009
(51) International Patent Classification (IPC): 
F01D 15/10(2006.01)
F02C 7/232(2006.01)
F02C 7/22(2006.01)
 F02C 9/26(2006.01)
F02C 9/28(2006.01)
(84) Designated Contracting States:
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR
Designated Extension States:
AL BA RS

(30) Priority: 05.02.2008 US 26230

(71) Applicant: General Electric Company
Schenectady, NY 12345 (US)

(72) Inventors:
  • Szepek, Scott William
    Glenville, NY 12302 (US)
  • Sweet, Bryan Edward
    Valatie, NY 12184 (US)
  • Buchalter, Lauren Jeanne
    Taylors, SC 29687 (US)
  • Stats, David Andrew
    Clifton Park, NY 12065 (US)
  • Mariani, Michael John
    Greer, SC 29650 (US)

(74) Representative: Bedford, Grant Richard 
GPO Europe GE International Inc. The Ark 201 Talgarth Road Hammersmith
London W6 8BJ
London W6 8BJ (GB)

   


(54) Gas turbine engine system


(57) A gas turbine engine system (10) is provided. The system includes an electrical generator (24) configured to provide electrical energy to a load, a gas turbine engine including at least one combustor (14) including a plurality of fuel injection points configured to receive a flow of fuel from a plurality of corresponding flow control devices, and a fuel control system (28). The fuel control system includes a plurality of sensors (26) positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor and a processor. The processor is programmed to receive a signal from at least one of the plurality of sensors indicative of a composition of the fuel, using a flow model and at least one signal, determine the physical properties of a fuel at an inlet (20) to the flow control devices, determine a corresponding correction to a gas fuel flow gain using the determined physical properties, and automatically control fuel delivery and fuel split between the fuel injection points on the combustor using the determined flow gain to facilitate permitting a relatively large variation in the fuel composition for use in the gas turbine engine.







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